Gas turbine system

ABSTRACT

A gas turbine system ( 1 A) includes a gas turbine unit ( 2 ) and a cooling fluid generator ( 5 ). The gas turbine unit ( 2 ) includes a first compressor ( 21 ) and a first expansion turbine ( 23 ) coupled to each other by a first shaft ( 22 ), a combustor ( 26 ), and a fuel tank ( 30 ). A fuel held in the fuel tank ( 30 ) circulates through a fuel circulation passage ( 31 ). A working fluid that has a pressure increased by the first compressor ( 1 ) is extracted from the gas turbine unit ( 2 ). The cooling fluid generator ( 5 ) includes a cooler ( 55 ) for cooling, with the fuel flowing through the fuel circulation passage ( 31 ), the working fluid that has been extracted from the gas turbine unit ( 2 ), and a second expansion turbine ( 53 ) for expanding the working fluid that has flowed out of the cooler ( 55 ).

TECHNICAL FIELD

The present invention relates to a gas turbine system including a gasturbine unit.

BACKGROUND ART

Conventionally, as a gas turbine system including a gas turbine unit,there has been known a cogeneration system that produces hot water, etc.by utilizing the waste heat caused when the gas turbine unit generateselectricity. In recent years, there also has been proposed a gas turbinesystem that directly produces hot water and cold air by using a gasturbine unit without generating electricity. For example, PatentLiterature 1 discloses a gas turbine system 100 as shown in FIG. 6.

The gas turbine system 100 includes a first compressor 101 and a firstexpansion turbine 102 coupled to each other by a shaft, a combustor 103,a regenerative heat exchanger 104, and a heat exchanger 123 for hotwater, as elements constituting a gas turbine unit. The first compressor101 compresses air taken from atmosphere. The air discharged from thefirst compressor 101 passes through the regenerative heat exchanger 104,and then flows into the combustor 104. A fuel is injected into thecombustor 104 and combusted therein. A combustion gas generated in thecombustor 104 heats the air to flow into the combustor 104 in theregenerative heat exchanger 104, and then flows into the first expansionturbine 102 to be expanded therein. The first expansion turbine 102creates power from the expanding combustion gas as a rotation torque todrive the first compressor 101. The combustion gas discharged from thefirst expansion turbine 102 is utilized, in the heat exchanger 123 forhot water, as a heat source for producing hot water, and then exhaustedinto the atmosphere.

In the gas turbine system 100, the gas turbine unit has no powergenerator. Thus, in order to start the gas turbine unit, the gas turbinesystem 100 is provided with a reciprocating type compressor 105 forsupplying compressed air to the combustor 104 at the time of starting.

Furthermore, the gas turbine system 100 has a configuration to extract,from the gas turbine unit, the air compressed in the first compressor101 and lower the temperature of this extracted air (so-called bleedair) so as to produce cold air. Specifically, the gas turbine system 100is provided with a first heat exchanger 121 for cooling the airextracted from the gas turbine unit with cold water, a second compressor111 for compressing the air that has flowed out of the first heatexchanger 121, a second heat exchanger 122 for cooling the airdischarged from the second compressor 111 with cold water, and a secondexpansion turbine 112 for expanding the air that has flowed out of thesecond heat exchanger 122. The second expansion turbine 112 is coupledto the second compressor 111 by a shaft, and creates power from theexpanding air as a rotation torque to drive the second compressor 111. Amoisture separator 113 for separating moisture from the air is providedbetween the second heat exchanger 122 and the second expansion turbines112. The water heated by cooling the air in the first heat exchanger 121and the second heat exchanger 122 is supplied to the heat exchanger 123for hot water in the gas turbine unit.

CITATION LIST Patent Literature

-   PTL 1: JP 4324719 B

SUMMARY OF INVENTION Technical Problem

The gas turbine system 100 disclosed in Patent Literature 1 producescold air. Accordingly, it is conceivable to incorporate the gas turbinesystem 100 in a vehicle, such as an automobile, to, for example, performinterior cooling of the vehicle by utilizing the cold air generated inthe gas turbine system 100. However, since the gas turbine system 100disclosed in Patent Literature 1 was developed on the assumption that itis placed in an environment where abundant cold water is available, itneeds additional equipment for holding cold water in the case of beingincorporated in a vehicle. Thus, the gas turbine system 100 is notsuitable to be incorporated in a vehicle that is required to bedownsized and light-weight.

In view of the foregoing, the present invention is intended to provide agas turbine system suitable to be incorporated in a vehicle.

Solution to Problem

In order to solve the above-mentioned problem, the present inventionprovides a gas turbine system including: a gas turbine unit including afirst compressor for compressing a working fluid, a combustor in which afuel is injected into the working fluid discharged from the firstcompressor so as to be combusted, a first expansion turbine forexpanding a combustion gas generated in the combustor, the firstexpansion turbine being coupled to the first compressor by a firstshaft, and a fuel tank for holding the fuel to be supplied to thecombustor; a fuel circulation passage that allows the fuel held in thefuel tank to circulate therethrough; and a cooling fluid generatorincluding a cooler for cooling, with the fuel flowing through the fuelcirculation passage, the working fluid that has a pressure increased bythe first compressor and that has been extracted from the gas turbineunit, and a second expansion turbine for expanding the working fluidthat has flowed out of the cooler.

Advantageous Effects of Invention

In the above-mentioned configuration, by cooling the working fluid byusing the fuel, it is possible to construct a system that does notrequire input except for the working fluid. Therefore, the presentinvention can realize a gas turbine system suitable to be incorporatedin a vehicle.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a configuration diagram of a gas turbine system according toEmbodiment 1 of the present invention.

FIG. 2 is a configuration diagram of a modification of the gas turbinesystem.

FIG. 3 is a configuration diagram of a gas turbine system according toEmbodiment 2 of the present invention.

FIG. 4 is a configuration diagram of a modification of the gas turbinesystem.

FIG. 5 is a configuration diagram of another modification of the gasturbine system.

FIG. 6 is a configuration diagram of a conventional gas turbine system.

DESCRIPTION OF EMBODIMENTS

Hereinafter, embodiments of the present invention are described indetail with reference to the drawings.

Embodiment 1

FIG. 1 shows a gas turbine system 1A according to Embodiment 1 of thepresent invention. The gas turbine system 1A is to be incorporated in avehicle (not shown), and includes a gas turbine unit 2, a cooling fluidgenerator 5, an air conditioning unit 6, and a heat exchanger 7 servingalso as a silencer. In the present embodiment, air is used as a workingfluid for the gas turbine unit 2 and the cooling fluid generator 5, andthe cold air generated in the cooling fluid generator 5 is utilizeddirectly for air conditioning.

The gas turbine unit 2 includes a first compressor 21 and a firstexpansion turbine 23 coupled to each other by a first shaft 22, acombustor 26, and a regenerative heat exchanger 27. In the presentembodiment, the regenerative heat exchanger 27 is provided from theviewpoint of enhancing the thermal efficiency of the gas turbine unit 2.However, the regenerative heat exchanger 27 may be omitted. The gasturbine unit 2 further includes a power generator 24 coupled to thefirst shaft 22, a control circuit 25 that is connected to the powergenerator 24 and includes an inverter, etc., and a fuel tank 30 forholding a fuel to be supplied to the combustor 26.

The first compressor 21 draws the air taken from the atmosphere andcompresses it. The power generator 24 is used as a motor at the time ofstarting, and rotates the first shaft 22 to drive the first compressor21. The high pressure air discharged from the first compressor 21 flowsinto the regenerative heat exchanger 27 and is heated therein withafter-mentioned combustion gas to have a further increased temperature,and then flows into the combustor 26.

In the combustor 26, the fuel from the fuel tank 30 is injected into thehigh pressure air through an after-mentioned fuel circulation passage31, and an air-fuel mixture is formed. The fuel injected into thecombustor 104 is fired by a spark electrode (not shown) and combusted.This allows the air-fuel mixture to be a high temperature combustion gaswhile keeping its pressure substantially.

The combustion gas generated in the combustor 26 flows into the firstexpansion turbine 23 and is expanded therein to have a pressure reducedto around an atmospheric pressure. The first expansion turbine 23creates power from the expanding combustion gas as a rotation torque todrive the first compressor 21 and provide the power generator 24 with aredundant power. Thereby, the power generator 24 generates electricity.The combustion gas discharged from the first expansion turbine 23 flowsinto the regenerative heat exchanger 27. In the regenerative heatexchanger 27, heat is exchanged between the combustion gas and the highpressure air to flow into the combustor 26, so that the temperature ofthe combustion gas is lowered. The combustion gas that has flowed out ofthe regenerative heat exchanger 27 flows into the heat exchanger 7 andis cooled therein with after-mentioned adjusted air so as to have afurther lowered temperature, and then exhausted into the atmosphere.

Both ends of the fuel circulation passage 31 are connected to the fueltank 30. The fuel held in the fuel tank 30 is circulated through thefuel circulation passage 31 that is provided with a pressure pump 31 a.In the present embodiment, a liquid fuel is held in the fuel tank 30.However, a gaseous fuel may be held in the fuel tank 30. Use of a liquidfuel has the advantage of reducing the volumetric capacity of the fueltank 30. Use of a gaseous fuel has the advantage of simplifying amechanism for injecting the fuel into the combustor 26. As the liquidfuel, an existing petroleum-derived fuel, such as gasoline and dieseloil (particularly a second-generation bio diesel fuel), that has beenused conventionally may be used. However, an alcohol fuel, such asmethanol and ethanol, or a alcohol-based composite fuel containing thealcohol fuel is preferred. As the gaseous fuel, CNG (Compressed NaturalGas), propane (LPG, standing for Liquefied Petroleum Gas), MTBE (MethylTertiary Butyl Ether), and hydrogen may be used, for example.

Table 1 shows the type-dependent properties of the above-mentionedliquid fuels and gaseous fuels (this is cited from: American PetroleumInstitute (API), Alcohols and Ethers, Publication No. 4261, 3rd ed.(Washington, D.C., June 2001), Table 2; Petroleum Product Surveys, MotorGasoline, Summer 1986, Winter 1986/1987. National Institute forPetroleum and Energy Research; and American Petroleum Institute (API),Alcohols and Ethers, Publication No. 4261, 3rd ed. (Washington, D.C.,June 2001), Table B-1. In the citation, the values are converted fromft/lb unit into SI unit.)

TABLE 1 Fuel type Gasoline No2 Diesel oil Methanol Chemical formula C4C12 C8 C25 CH₃OH Molecular weight 100 105 200 200 32.04 Specific weight0.72 0.780 0.850 0.850 0.796 Density kgf/m³ 720 780 849 849 795 Boilingpoint ° C. 26.7 225 180 340 65.0 Vapor pressure (37.8° C.) MPa 0.005630.0106 0.000141 0.000141 0.00324 Lower heating value KJ/kg 43401 4340142746 42746 20072 Higher heating value KJ/kg 46488 46488 45718 4571822860 Evaporation heat (15.8° C.) KJ/kg 349 349 232 232 1176 Fuel typeEthanol MTBE Propane CNG Hydrogen Chemical formula C₂H₅OH (CH₃)₃COCH₃C₃H₈ CH₄C₂H₆ H₂ Molecular weight 46.07 88.15 44.1 16.04 2.02 Specificweight 0.794 0.744 0.508 0.424 0.07 Density kgf/m³ 793 742 506 128 —Boiling point ° C. 77.8 55.0 −42.2 −164 −253 Vapor pressure (37.8° C.)MPa 0.00162 0.00549 0.146 1.69 — Lower heating value KJ/kg 26923 3507046246 47089 121348 Higher heating value KJ/kg 29816 37917 50183 52169138984 Evaporation heat (15.8° C.) KJ/kg 920 390 449 509 446

The fuel circulation passage 31 serves to form, outside the gas turbineunit 2, a route through which the fuel flows. The fuel circulationpassage 31 passes through the cooling fluid generator 5. Usually, thefuel in the fuel tank 30 has a temperature comparable to an atmospherictemperature. This fuel is used as a heat medium for removing heat in thecooling fluid generator 5. Thus, the fuel circulation passage 31 isprovided with a fuel cooler 32 for cooling the fuel flowing through thefuel circulation passage 31 as a means to prevent the fuel from beingoverheated. The fuel cooler 32 in the present embodiment is configuredto cool the fuel with wind W generated by travelling of the vehicle.Preferably, the fuel cooler 32 is placed at a position immediatelydownstream of the fuel tank 30 or immediately downstream of the pressurepump 31 a, to which the wind W is introduced easily. The fuel cooler 32may be omitted depending on the capacity of the fuel tank 30.

In the present embodiment, the fuel circulation passage 31 is configuredto pass through the control circuit 25 as well as the power generator24. Thus, the control circuit 25 and the power generator 24 are cooledwith the fuel flowing through the fuel circulation passage 31.Preferably, the fuel cooler 32 is disposed on an upstream side of thepower generator 24 and the control circuit 25 as in the illustratedexample.

The cooling fluid generator 5 includes a second compressor 51 and asecond expansion turbine 53 coupled to each other by a second shaft 52,a cooler 55, and a moisture separator 56. The cooling fluid generator 5further includes a power generator 54 coupled to the second shaft 52.

One end of a bleed air passage 4 for extracting from the gas turbineunit 2 the air having a pressure increased by the first compressor 21 isconnected to the second compressor 51. In the present embodiment, theother end of the bleed air passage 4 is connected to an intermediatepressure position of the first compressor 21 so that the air beingcompressed in the first compressor 21 is supplied to the secondcompressor 21 through the bleed air passage 4.

The bleed air passage 4 is provided with a flow control valve 41. Theflow control valve 41 is opened when the temperature of the air that hasbeen extracted from the gas turbine unit 2 through the bleed air passage4 and has a pressure increased by the first compressor 21 (hereinaftersimply referred to as a “bleed air”) reaches a specified temperaturedetermined based on the pressure ratio of the second compressor 22.

The second compressor 51 draws the bleed air and compresses it. Thepower generator 54 is used as a motor at the time of starting, androtates the second shaft 52 to drive the second compressor 51. The highpressure air discharged from the second compressor 51 flows into thecooler 55. In the cooler 55, heat is exchanged between the high pressureair and the fuel flowing through the fuel circulation passage 31 so thatthe high pressure air is cooled with the fuel.

The high pressure air that has flowed out of the cooler 55 flows intothe second expansion turbine 53 and is expanded therein to have apressure reduced to around an atmospheric pressure. This expansion inthe second expansion turbine 53 produces cold air (cooling fluid). Thesecond expansion turbine 53 creates power from the expanding air as arotation torque to drive the second compressor 51 and provide the powergenerator 54 with a redundant power. Thereby, the power generator 54generates electricity. Under the operating condition in which there isno redundant power, it also is possible to use the power generator 54merely as a motor. The air discharged from the second expansion turbine53 passes through the moisture separator 56, and then is sent to the airconditioning unit 6. The moisture separator 56 separates moisture fromthe air discharged from the second expansion turbine 53.

The air conditioning unit 6 includes a mixer 62 connected to the secondexpansion turbine 53 via the moisture separator 56, and a blower 61 fortaking air from the atmosphere and supplying it to the mixer 62. The airdischarged from the second expansion turbine 53 is adjusted to have adesired temperature by being mixed, in the mixer 62, with the airsupplied from the blower 61. This adjusted air is sent to the heatexchanger 7. However, during interior cooling, the adjusted airadjusted, in the air conditioning unit 6, to have a temperature inaccordance with a temperature required for air conditioning may besupplied directly to the inside of the vehicle (not shown) withoutpassing through the heat exchanger 7.

The heat exchanger 7 exchanges heat between the adjusted air that hasflowed out of the mixer 62 and the above-mentioned combustion gas thathas flowed out of the regenerative heat exchanger 27 so as to heat theadjusted air that has flowed out of the mixer 62 to have a temperaturesuitable for air conditioning. The air heated in the heat exchanger 7 issupplied to the inside of the vehicle (not shown).

As described above, in the present embodiment, the mixer 62 of the airconditioning unit 6 and the heat exchanger 7 constitute a temperatureadjuster for adjusting the temperature of the air discharged from thesecond expansion turbine 56.

When the operation of the gas turbine system 1A described above isviewed from the fuel side, the fuel with a flow rate sufficiently higherthan the flow rate necessary for the combustion in the combustor 26 isallowed to flow into the fuel circulation passage 31 by the pressurepump 31 a. The flow rate of the fuel flowing through the fuelcirculation passage 31 is determined based on the amount of heatrequired for cooling in the control circuit 25, the power generator 24and the cooler 55 so that the temperature of the fuel is increased by anappropriate value. The fuel flowing through the fuel circulation passage31 is heated in the control circuit 25 and the power generator 24 in thecourse of being sent from the fuel tank 30 to the cooler 55, and heatedfurther in the cooler 55, and then returned to the fuel tank 30. A partof the fuel flowing through the fuel circulation passage 31 is suppliedto the combustor 26 in the course of returning from the cooler 55 to thefuel tank 30.

In the present embodiment, a part of the fuel flowing through the fuelcirculation passage 31 is supplied to the combustor 26, and thus thepressure pump 31 a increases the pressure of the fuel to a pressure thatenables the fuel to be injected. However, it also is possible to providea jet pump to a flow passage through which the fuel is guided from thefuel circulation passage 31 to the combustor 26 so as to reduce thevalue by which the pressure pump 31 a increases the pressure of thefuel.

The combustion of the fuel in the combustor 26 occurs after thetemperature of the air-fuel mixture composed of the fuel and the airreaches a temperature suitable for the combustion. In the presentembodiment, since the fuel heated in the control circuit 25, the powergenerator 24 and the cooler 55 is supplied to the combustor 26, theamount of heat necessary to heat the air-fuel mixture to an appropriatetemperature in the combustor 26 can be reduced by the value of thetemperature increase in the fuel heated.

Next, operating points in the case of using ethanol as the fuel aredescribed as examples. The precondition is that the atmospherictemperature is 15° C., the atmospheric pressure is 0.103 MPa, and thetype-dependent properties of ethanol shown in Table 1 are used.

Although the fuel has chemical energy, this energy cannot be utilized asit is. Thus, the fuel is combusted so that the chemical energy isconverted into thermal energy, and this thermal energy is utilizedeffectively.

The amount of heat measured when a unit quantity (1 kg, 1 m³ or 1 L) ofa fuel placed in a constant state (at 1 atmosphere and 25° C., forexample) is combusted completely with a sufficient amount of dry air andthe combustion gas is cooled to the original temperature (25° C. in thiscase) is referred to as a calorific value.

A calorific value including a condensation latent heat obtained when thewater vapor produced in a combustion gas is condensed is referred as ahigher calorific value. A calorific value in the case where the watervapor remains as it is and no condensation latent heat is includedtherein is referred to as a lower calorific value. The lower calorificvalue is obtained by subtracting the condensation latent heat of thewater vapor from the higher calorific value measured by a calorimeter.The lower calorific value is calculated by (Formula 1) below. Thethermal efficiency on the side of the power generator of the gas turbineunit 2 described hereinafter is calculated from the lower calorificvalue excluding the condensation latent heat of the water vapor.

Lower calorific value=Higher calorific value−Condensation latent heat ofwater vapor×Amount of water vapor  (Formula 1)

In the gas turbine unit 2, the outlet temperature of the firstcompressor 21 is about 190° C., the primary-outlet temperature of theregenerative heat exchanger 27 is about 810° C., the outlet temperatureof the combustor 26 is about 1200° C., the outlet temperature of thefirst expansion turbine 23 is about 910° C., and the secondary-outlettemperature of the regenerative heat exchanger 27 is about 340° C. Whenthe pressure is decreased from about 0.38 MPa to about 0.11 MPa in thefirst expansion turbine 23, 18 kW of electricity is generated.

In the cooling fluid generator 5, the bleed air temperature is about100° C., the outlet temperature of the second compressor 51 is about160° C., the outlet temperature of the cooler 55 is about 65° C., theoutlet temperature of the second expansion turbine 53 is about 3.0° C.When the pressure is decreased from about 0.33 MPa to about 0.12 MPa inthe first expansion turbine 23, 1.6 kW of electricity is generated.

The fuel is pumped at 0.4 MPa. The fuel has a temperature of about 25°C. at the inlet of the cooler 55 and a temperature of about 32° C. atthe outlet of the cooler 55.

The above-mentioned operating points are calculation results in the caseof using ethanol as the liquid fuel. However, it can be changed to adifferent fuel.

Usually, a gas turbine system is designed so that the required power(the amount of electricity generated by the power generator 24) isconstant. In the case of using a different fuel other than ethanol, theamount of electricity generated by the power generator 24 is maintainedby controlling the flow rate of the fuel to be supplied to the combustor26 so that the calorific value of the gas turbine unit 2 is equal to thecalorific value in the case of using ethanol. For example, in the casewhere the fuel is changed from ethanol to diesel oil (C25), the amountof the fuel to be supplied is controlled so as to be 0.70 times of thatin the case of using ethanol, based on the conversion of the lowercalorific value in Table 1.

As described above, it is possible to maintain the amount of electricitygenerated by the power generator 24 and the temperature of the bleed airto the cooling fluid generator 5 by setting the calorific value per unittime of the fuel supplied to the gas turbine unit 2 to be constant andsetting the amount of the atmosphere drawn into the gas turbine unit 2to be constant.

The temperature control in cooling the bleed air in the cooling fluidgenerator 5 is performed by controlling the heat transmissibility by theflow rate of the fuel circulating through the cooling fluid generator 5.

Next, based on the above-mentioned study results, the capacitiesrequired for each element constituting an electric vehicle and arefrigerator truck (at a moderate temperature of −5 to 5° C.) arestudied with reference to examples. Ethanol is used as the fuel.

Design Example 1 Electric Vehicle

Interior cooling capacity: Amount of air blow 350 m³/h, 4500 W

Interior heating capacity: Amount of air blow 450 m³/h, 5000 W

Rated output of power generator: 15 kW

In Design Example 1, the rated output of the power generator isdetermined to be 15 kW under the conditions that a secondary batterywith a power of 16 kWh is mounted on an electric vehicle (equivalent toa 1500 to 2000 cc passenger car) and this secondary battery is chargedwithin about 1 hour. As for the air conditioning capacity, the amount ofair blow is 350 m³/h in interior cooling and the interior coolingcapacity is 4500 W, and the amount of air blow is 450 m³/h in interiorheating and the interior heating capacity is 5000 W.

In this case, the flow rate of the working fluid in the gas turbine unit2 (the flow rate of the working fluid drawn into the first compressor21) is 0.135 kg/sec at the minimum.

When the above-mentioned results are applied to a truck with a totalpiston displacement of 3000 cc, the rated output of the power generatoris almost doubled to 30 kW, and the flow rate of the working fluid inthe gas turbine unit 2 (the flow rate of the working fluid drawn intothe first compressor 21) is 0.27 kg/sec at the minimum.

The above-mentioned study results reveal that the gas turbine system 1Ain the present embodiment can be applied to electric vehicles.

Design Example 2 Refrigerator Truck at Moderate Temperature

Refrigerating capacity: 0° C., 3000 W

Rated output of power generator: 30 kW

In Design Example 2, use of the gas turbine system for air conditioningin a cool box of a refrigerator truck is studied. As mentioned above,the air conditioning capacity (refrigerating capacity) of therefrigerator truck in Design Example 2 is smaller than that of thepassenger car in Design Example 1. This is because the cool box hasgreater heat insulation property than that of the passenger car, and isnot affected by the amount of solar radiation as it has no window.

Assuming that the refrigerator truck is equivalent to a truck with atotal piston displacement of 3000 cc, the truck is under severer travelcondition than that of the passenger car considering its loadingcapacity, and is presumed to consume a larger amount of electric power.Thus, the output of electricity generation needs to be increased aswell. In this case, it is possible to apply the gas turbine system 1A inthe present embodiment to the refrigerator truck by setting the ratedoutput of power generator to 30 kW and setting the flow rate of theworking fluid in the gas turbine unit 2 (the flow rate of the workingfluid drawn into the first compressor 21) to 0.27 kg/sec.

As described above, in the gas turbine system 1A in the presentembodiment, the bleed air extracted from the gas turbine unit 2 iscooled with the fuel, which makes it possible to generate cold energywith a small system. Particularly, in the present embodiment, since thegas turbine unit 2 includes the power generator 24, and the temperatureof the air discharged from the second expansion turbine 56 is adjustedby the temperature adjuster (the mixer 62 and the heat exchanger 7), itis possible to perform air conditioning while generating electricity.Therefore, when the gas turbine system 1A is incorporated in, forexample, an electric vehicle, both of the battery charge and the airconditioning can be realized.

For the electric vehicle, for example, it is proposed to heat the airinside the vehicle while circulating it in order to perform interiorheating efficiently. However, since the air inside the vehicle containsmoisture derived from a passenger, windows may be fogged when theinterior heating is performed while the air is circulated. In contrast,in the present embodiment, since the air dehumidified by the moistureseparator 56 is supplied to the inside of the vehicle, it is possible toprevent the fogging of the windows even during the interior heating andensure the field of view for the driver. As shown in FIG. 2, the gasturbine unit 2 may be provided with a flow passage 20 for taking the airfrom the inside of the vehicle so that the first compressor 21 draws anair mixture in which the air from the atmosphere and the air from theinside of the vehicle are mixed. Such a configuration makes it possibleto perform the interior heating while dehumidifying the air inside thevehicle.

Moreover, in FIG. 2, by providing a flow control valve (not shown) to aflow passage for taking the atmosphere outside the car into the firstcompressor 21 and providing a flow control valve (not shown) to the flowpassage 20, it is possible to adjust the flow rate of the atmospheretaken from the outside of the car and the flow rate of the air takenfrom the inside of the vehicle. Such a configuration makes it possibleto adjust the openings of these two flow control valves in accordancewith the atmospheric temperature and the temperature and humidity insidethe vehicle so as to dehumidify quickly the air in the vehicle.

Embodiment 2

Next, with reference to FIG. 3, a gas turbine system 1B according toEmbodiment 2 of the present invention is described. In the presentembodiment, the same components as those in Embodiment 1 are designatedby the same reference numerals, and the descriptions thereof areomitted.

In the present embodiment, the liquid fuel is held in the fuel tank 30,and the fuel circulation passage 31 is provided with a branch passage 34that branches from the fuel circulation passage 31 on an upstream sideof the cooler 55 and that reaches the combustor 26. Specifically, thefuel circulation passage 31 is provided with a distributing valve 33 onthe upstream side of the cooler 55, and an upstream end of the branchpassage 34 is connected to the distributing valve 33.

As the fuel used in the present embodiment, a fuel having a low boilingpoint under an atmospheric pressure and having a high steam pressurewhen being superheated is preferred. Specifically, an alcohol fuel, suchas methanol and ethanol, or an alcohol-based composite fuel containingthe alcohol fuel is preferred from the view point of the thermalefficiency of the gas turbine unit 2, the pressure ratio of the secondcompressor 51, and the superheat temperature necessary to obtain asufficient fuel vapor pressure. However, an existing petroleum-derivedfuel, such as gasoline and diesel oil, that has been used conventionallymay be used as long as it satisfies the above-mentioned selectionconditions. However, the alcohol fuel or the alcohol-derived compositefuel is particularly preferable in the present embodiment because thesefuels have a greater ability to cool the bleed air as they have a largerevaporation heat than that of the existing petroleum-derived fuel.

Moreover, the cooling fluid generator 5 is provided, on the upstreamside of the cooler 55, with a vaporizer 57 for vaporizing the fuelflowing through the branch passage 34 with the air discharged from thesecond compressor 51.

Furthermore, the branch passage 34 is provided, on a downstream side ofthe vaporizer 57, with a pressure accumulator 35 and a flow controlvalve 36 in this order.

Next, the operation of the gas turbine system 1B is described. Theoperation of the gas turbine unit 2 is the same as that described inEmbodiment 1.

The operation of the cooling fluid generator 5 is the same as thatdescribed in Embodiment 1, except for the following two points. Firstly,the air discharged from the second compressor 51 flows into thevaporizer 57 and is cooled therein by exchanging heat with the fuelflowing through the branch passage 34. Secondly, the flow control valve41 is opened when the temperature of the bleed air reaches a specifiedtemperature determined based on the pressure ratio of the secondcompressor 22 and the evaporating temperature of the fuel.

The distributing valve 33 distributes the fuel flowing through the fuelcirculation passage 31 to a circulation side to return to the fuel tank30 through the cooler 55, and to a combustion side to be supplied to thecombustor 26 through the vaporizer 57. The flow rate of the fueldistributed to the combustion side is equivalent to or slightly higherthan the flow rate necessary for the combustion in the combustor 26. Theflow rate of the fuel distributed to the circulation side is notparticularly limited and it can be high. The distribution ratio thusdetermined makes it possible to vaporize quickly the fuel with a lowflow rate, and increase the pressure of the vapor to a superheated stateand minimize the volumetric capacity necessary for the pressureaccumulator 35.

The fuel distributed to the circulation side is heated in the cooler 55,and then returned to the fuel tank 30. On the other hand, the fueldistributed to the fuel side flows into the vaporizer 57. In thevaporizer 57, the fuel is vaporized by exchanging heat with the highpressure air discharged from the second compressor 51, and obtains afurther increased temperature to reach a superheated state. In otherwords, the fuel lowers, by the evaporation heat, the temperature of thehigh pressure air discharged from the second compressor 51. The fuelthat has flowed out of the vaporizer 57 is once kept in the pressureaccumulator 35 and flows into the combustor 26 against the pressure inthe combustor 26 due to the vapor pressure of the fuel itself, accordingto the setting of the flow control valve 36.

In a common gas turbine unit, the pressure of a fuel is increased to apressure that enables the fuel to be injected by a pump or a compressor,and the fuel is supplied to a combustor, regardless of whether the fuelis a liquid fuel or a gaseous fuel. In contrast, in the gas turbinesystem 1B in the present embodiment, it is unnecessary to increase thepressure of the fuel to a pressure that enables the fuel to be injectedby a pump, and it is possible to increase the pressure of the fuel tothe pressure that enables the fuel to be injected by gasifying the fuel.That is, the heat emitted from the air in the vaporizer 57 of thecooling fluid generator 5 is used as the pressure source for injectingthe fuel. Such a configuration makes it possible to inject the fuel witha simple device such as an on-off valve.

Next, operating points in the case of using ethanol (with a boilingpoint of 78° C. under an atmospheric pressure) as the fuel are describedas examples. The precondition is that the atmospheric temperature is 15°C., the atmospheric pressure is 0.103 MPa, and the type-dependentproperties of ethanol shown in Table 1 are used.

The operating points for the gas turbine unit 2 are the same as inEmbodiment 1. The operating points for the cooling fluid generator 5 arethe same as in Embodiment 1, except that the outlet temperature of thevaporizer 57 is about 120° C.

The fuel is pumped at 0.4 MPa. The fuel has a temperature of about 25°C. at the inlet of the cooler 55 and at the inlet of the vaporizer 57, atemperature of about 26° C. at the outlet of the cooler 55, and atemperature of about 120° C. at the outlet of the vaporizer 57. As forthe distribution ratio, about 99% of the fuel is distributed to thecirculation side and about 1% of the fuel is distributed to thecombustion side.

As described above, the gas turbine system 1B in the present embodimentcan achieve an output comparable to that of the gas turbine system 1A inEmbodiment 1. Therefore, it is needless to say that the gas turbinesystem 1B can be applied to the electric vehicle and the refrigeratortruck as in Design Example 1 and Design Example 2 described inEmbodiment 1.

In the gas turbine system 1B in the present embodiment, since the bleedair extracted from the gas turbine unit 2 is cooled by utilizing thelatent heat of the fuel, it is possible to use a smaller heat exchangerthan in the case, such as in Embodiment 1 in which the gaseous fuel isused, where heat is exchanged between gases each having a low heattransfer coefficient.

Moreover, since the gas turbine system 1B is capable of supplying thevaporized fuel to the combustor 26 while holding the liquid fuel in thefuel tank 30, it is possible to obtain both of the advantage of theliquid fuel that allows the fuel tank 30 to have a reduced volumetriccapacity and the advantage of the gaseous fuel that allows the mechanismfor injecting the fuel into the combustor 26 to be simplified.Furthermore, in the present embodiment, the power of the pressure pump31 a can be smaller than in Embodiment 1 because it is unnecessary toincrease the pressure of the fuel to a pressure that enables the fuel tobe injected by the pressure pump 31 a. For example, in the case whereethanol is used as the fuel, the power of the pressure pump 31 a, whichneeds to be 100 W in Embodiment 1, can be reduced to 22.5 W in thepresent embodiment.

Moreover, when air conditioning is necessary even in the case where noelectricity is generated in the gas turbine unit 2, that is, even in thecase where it is unnecessary to combust the fuel, it is possible to stopunnecessary generation of the evaporated fuel by setting the ratio ofthe distribution by the distributing valve 33 so that 0% of the fuel isdistributed to the combustion side and 100% of the fuel is distributedto the circulation side.

<Modification>

In Embodiment 2, the other end of the bleed air passage 4 is connectedto the intermediate pressure position of the first compressor 21. Inorder to enhance the thermal efficiency of the gas turbine unit 2, it iseffective to reduce the power of the first compressor 21. To realizethis, it is preferable to extract the air being compressed in the firstcompressor 21 as the bleed air.

On the other hand, in order to lower further the temperature of the airdischarged from the second expansion turbine 53 in the cooling fluidgenerator 5, it is preferable that the air discharged from the secondcompressor 51 has a high pressure. Thus, in the case where the cold airgenerating capacity of the cooling fluid generator 5 is considered to bemore important than the thermal efficiency of the gas turbine unit 2,the compressed air in the first compressor 21 may be extracted as thebleed air. Specifically, as shown in FIG. 4, the other end (upstreamend) of the bleed air passage 4 may be connected to a flow passagebetween the first compressor 21 and the regenerative heat exchanger 27.

In Embodiment 2, the fuel circulation passage 31 is provided with thefuel cooler 32, taking into account the heat transmissibility on thefuel side. However, in the case where the flow velocity of the fuel ishigh also in the fuel tank 30 because the circulation amount of the fuelis large, and the wind W generated by the travelling of the vehicle canbe taken to the vicinity of the fuel tank 30, the fuel cooler 32 may beprovided to the fuel tank 30 so as to cool the fuel held in the fueltank 30 as shown in FIG. 5.

The modifications shown in FIG. 4 and FIG. 5 can be applied also toEmbodiment 1.

Other Embodiments

Although the temperature of the air discharged from the second expansionturbine 56 is adjusted in the mixer 62 and the heat exchanger 7 in eachgas turbine system 1A and 1B in Embodiments above, the temperatureadjuster for controlling the temperature of the air discharged from thesecond expansion turbine 56 is not limited to this. For example, thetemperature adjuster may be a configuration in which a bypass passage isprovided to the bleed air passage 4 to mix the bleed air with the airdischarged from the second expansion turbine 56.

It also is possible to omit the temperature adjuster and utilizedirectly, for an application such as refrigeration, the air dischargedfrom the second expansion turbine 56. Alternatively, when the air is notused as the working fluid, it is possible to allow the working fluiddischarged from the second expansion turbine 56 to flow into a heatexchanger for various applications.

Although the second expansion turbine 53 is coupled to the secondcompressor 51 by the second shaft 52 in Embodiments above, it also ispossible to divide the second shaft 52 so that a motor is provided onthe second compressor 51 side and the power generator is provided on thesecond expansion turbine 53 side of the second shaft 52, and rotate thesecond compressor 51 and the second expansion turbine 53 at appropriaterotation speeds, respectively.

Furthermore, it also is possible to omit the second compressor 51 whenthe pressure of the air extracted from the gas turbine unit 2 issufficiently high. However, the presence of the second compressor 51makes it possible to ensure a high expansion ratio in the secondexpansion turbine 53.

Moreover, although the fuel cooler 32 is configured to cool the fuelwith the wind generated by the travelling of the vehicle in Embodimentsabove, the fuel cooler 32 may be, for example, a fan when the gasturbine systems 1A and 1B are not incorporated in vehicles.

The gas turbine systems 1A and 1B in Embodiments above can be downsizedbecause they can generate cold energy as long as the working fluidexists besides the fuel. Therefore, the gas turbine systems 1A and 1Bare not only suitable to be incorporated in vehicles but also useful asstationary gas turbine systems. The gas turbine unit 2 may not have thepower generator 24 depending on the applications for which the gasturbine systems 1A and 1B are used.

1. A gas turbine system comprising: a gas turbine unit including a firstcompressor for compressing a working fluid, a combustor in which a fuelis injected into the working fluid discharged from the first compressorso as to be combusted, a first expansion turbine for expanding acombustion gas generated in the combustor, the first expansion turbinebeing coupled to the first compressor by a first shaft, and a fuel tankfor holding the fuel to be supplied to the combustor; a fuel circulationpassage that allows the fuel held in the fuel tank to circulatetherethrough; and a cooling fluid generator including a cooler forcooling, with the fuel flowing through the fuel circulation passage, theworking fluid that has a pressure increased by the first compressor andthat has been extracted from the gas turbine unit, and a secondexpansion turbine for expanding the working fluid that has flowed out ofthe cooler.
 2. The gas turbine system according to claim 1, wherein theworking fluid is air, and the gas turbine system further comprises atemperature adjuster for adjusting a temperature of the air dischargedfrom the second expansion turbine.
 3. The gas turbine system accordingto claim 2, wherein the gas turbine unit further includes a regenerativeheat exchanger for exchanging heat between the combustion gas dischargedfrom the first expansion turbine and the air to flow into the combustor,and the temperature adjuster includes a mixer for mixing the airdischarged from the second expansion turbine with air taken fromatmosphere, and a heat exchanger for exchanging heat between the airthat has flowed out of the mixer and the combustion gas that has flowedout of the regenerative heat exchanger.
 4. The gas turbine systemaccording to claim 1, wherein the cooling fluid generator furtherincludes a second compressor for compressing the working fluid that hasa pressure increased by the first compressor, before the working fluidflows into the cooler.
 5. The gas turbine system according to claim 4,wherein the second expansion turbine is coupled to the second compressorby a second shaft.
 6. The gas turbine system according to claim 4,wherein a liquid fuel is held in the fuel tank, the fuel circulationpassage is provided with a branch passage that branches from the fuelcirculation passage on an upstream side of the cooler and that reachesthe combustor, and the cooling fluid generator further includes avaporizer for vaporizing the fuel flowing through the branch passagewith the working fluid discharged from the second compressor.
 7. The gasturbine system according to claim 6, wherein the branch passage isprovided, on a downstream side of the vaporizer, with a pressureaccumulator.
 8. The gas turbine system according to claim 1, wherein thecooling fluid generator further includes a moisture separator forseparating moisture from the working fluid discharged from the secondexpansion turbine.
 9. The gas turbine system according to claim 1,further comprising a fuel cooler for cooling the fuel held in the fueltank or the fuel flowing through the fuel circulation passage.
 10. Thegas turbine system according to claim 9, wherein the gas turbine systemis to be incorporated in a vehicle, and the fuel cooler cools the fuelwith wind generated by travelling of the vehicle.
 11. The gas turbinesystem according to claim 1, wherein the gas turbine unit furtherincludes a power generator coupled to the first shaft.
 12. The gasturbine system according to claim 11, wherein the fuel circulationpassage is configured to pass through the power generator.